Investigation of Aerodynamic Characteristics in Pitch and Sideslip of a 45 Degree Sweptback-Wing Airplane Model With Various Vertical Locations of Wing and Horizontal Tail: Basic-Data Presentation, M = 2.01

Memorandum presenting an investigation conducted in the 4- by 4-foot supersonic pressure tunnel to determine the effects of vertical location of wing and horizontal tail on the aerodynamic characteristics in combined pitch and sideslip of a supersonic airplane configuration at a Mach number of 2.01. The configurations investigated included a high-wing, a midwing, and a low-wing arrangement, each with four horizontal-tail locations.